公开(公告)号：US4799385A

公开(公告)日：1989-01-24

申请号：US72235

申请日：1987-07-10

Applicant: Rand H. Hulsing ,  Rex B. Peters

Inventor： Rand H. Hulsing ,  Rex B. Peters

IPC: G01C19/5726 ,  G01P9/04

CPC classification number: G01C19/5726

Abstract: A Coriolis rate sensor comprising first and second accelerometers mounted with their force sensing axes parallel to a common sensing axis. The accelerometers are vibrated along arcs in response to a periodic drive signal at a first frequency, each arc being tangent to a vibration axis normal to the sensing axis. The accelerometer output signals are demodulated to determine angular rate, as well as to detect the phase shift between the drive signal and the periodic compounds of the output signals. In one arrangement, the detected phase shifts are used to drive a phase servo that tends to reduce the bias error caused by interaction between the phase shifts and misalignments of the accelerometers with respect to the sensing axis. In another arrangement, the phase shifts are used to calculate a bias term for correcting the measured angular rate. A single accelerometer embodiment is also described.

Abstract translation: 科里奥利速率传感器包括第一和第二加速度计，其安装有其感测轴平行于公共传感轴。 响应于第一频率的周期性驱动信号，加速度计沿弧线振动，每个弧与垂直于感测轴的振动轴相切。 加速度计输出信号被解调以确定角速率，以及检测驱动信号和输出信号的周期性化合物之间的相移。 在一种布置中，检测到的相移被用于驱动相位伺服，该相位伺服倾向于减小由加速度计相对于感测轴的相移和不对准之间的相互作用引起的偏移误差。 在另一种布置中，使用相移来计算用于校正测量的角速率的偏差项。 还描述了单个加速度计实施例。

公开(公告)号：US4792799A

公开(公告)日：1988-12-20

申请号：US62368

申请日：1987-06-12

Applicant: Michael M. Grove

Inventor： Michael M. Grove

IPC: G01C21/00 ,  B64D45/04 ,  G01C5/00 ,  G05D1/08 ,  G08B23/00

CPC classification number: G01C5/005

Abstract: A ground proximity warning system especially adapted for a tactical aircraft provides the pilot with a warning in the event that the closure rate is excessive for the altitude above ground at which the aircraft is flying. The descent rate of the aircraft is monitored and used to bias the closure rate warning signal to reduce nuisance warnings when the excessive closure rate is part of an intentional maneuver such as a dive during a tactical mission.

Abstract translation: 特别适用于战术飞机的地面接近警报系统为飞行员飞行员在飞机飞越地面高度的关闭率过大时提供警告。 监视和使用飞机的下降率来偏离关闭速率警告信号，以在过度关闭速率是有意的操纵（例如在战术任务期间的潜水）的一部分时减少妨扰警告。

公开(公告)号：US4786861A

公开(公告)日：1988-11-22

申请号：US91977

申请日：1987-09-01

Applicant: Rand H. Hulsing, II ,  Charles K. Lee

Inventor： Rand H. Hulsing, II ,  Charles K. Lee

IPC: G01R23/14 ,  G01R23/10 ,  G01R23/02

CPC classification number: G01R23/10

Abstract: A device and method for measuring the frequency of an input signal by measuring the number of cycles of the input signal that occur in a sample interval between successive sampling times t.sub.n. An integer counter determines an estimated integer number of input signal cycles, and fraction counters determine fractional counts by counting cycles of a clock signal during time intervals between a first measurement time before the sampling time and a second measurement time after the sampling time. A correction circuit refines the fractional counts by determining the phase relationships between the clock and input signals at each measurement time. The correction circuit includes a constant current source, a capacitor, a first switch connected between the constant current source and a reference potential, a second switch connected between the constant current source and the capacitor, and a control circuit for the switches. The control circuit disconnects the current source from the reference potential at each measurement time, and disconnects the current source from the capacitor upon the next occurance of a periodic characteristic of the clock signal that occurs after the measurement time. The voltage on the capacitor then provides the required phase relationship.

Abstract translation: 一种用于通过测量在连续采样时间tn之间的采样间隔中发生的输入信号的周期数来测量输入信号的频率的装置和方法。 整数计数器确定输入信号周期的估计整数，分数计数器通过在采样时间之前的第一测量时间与采样时间之后的第二测量时间之间的时间间隔期间计数时钟信号的周期来确定分数计数。 校正电路通过在每个测量时间确定时钟和输入信号之间的相位关系来优化分数计数。 校正电路包括恒流源，电容器，连接在恒流源和参考电位之间的第一开关，连接在恒流源和电容器之间的第二开关，以及用于开关的控制电路。 控制电路在每个测量时间将电流源与参考电位断开，并且在测量时间之后发生的时钟信号的周期性特征的下一次发生时将电流源与电容器断开。 电容器上的电压然后提供所需的相位关系。

公开(公告)号：US4783742A

公开(公告)日：1988-11-08

申请号：US948100

申请日：1986-12-31

Applicant: Rex B. Peters

Inventor： Rex B. Peters

IPC: E21B47/022 ,  E21B47/00 ,  G01C9/08

CPC classification number: E21B47/022

Abstract: Disclosed is an inertial navigation borehole survey system wherein the signals supplied by accelerometers (40) that are contained within the borehole survey system probe (10) are corrected for gravitational gradients encountered as the probe (10) travels through a borehole (12). The gravity correction is effected in the survey system signal processor (24) and is based on a gravity gradient signal that mathematically corresponds to: ##EQU1## where f represents the specific force due to gravity; f.sub.o represents the specific force of gravity at wellhead (20) of borehole (12); R.sub.o represents the average radius of the earth; .rho.(H) represents the local density of the geological formation penetrated by the borehole as a function of depth H; and .rho..sub.ave represents the means density of the earth. In utilizing the gravitational gradient to generate a gravity correction signal, the signal processor (24) effects a summation process that mathematically corresponds to: ##EQU2## where (.DELTA.H).sub.i represents the depth change between the "ith" signal processing cycle and the nextmost antecedent processing cycle, and, the summation range extends from the first signal processing cycle performed during the borehole survey through the final signal processing cycle of the borehole survey operation.

Abstract translation: 公开了一种惯性导航钻孔测量系统，其中由探测器（10）行进通过钻孔（12）所遇到的重力梯度校正了包含在钻孔测量系统探头（10）内的由加速度计（40）提供的信号。 重力校正在测量系统信号处理器（24）中实现，并且基于数学上对应于：的重力梯度信号，其中f表示由重力引起的特定力; fo表示井眼（20）的井口（20）的比重力; Ro代表地球的平均半径; rho（H）表示作为深度H的函数的钻孔渗透的地质构造的局部密度; 而rho ave代表地球的平均密度。 在利用重力梯度来产生重力校正信号的情况下，信号处理器（24）实现数学上对应于以下的求和过程：其中（DELTA H）i表示“第i”个信号处理周期与 最后的前期处理周期，总和范围从钻孔测量期间执行的第一个信号处理周期延伸到井眼测量操作的最终信号处理周期。

公开(公告)号：US4782700A

公开(公告)日：1988-11-08

申请号：US75039

申请日：1987-07-17

Applicant: Rand H. Hulsing

Inventor： Rand H. Hulsing

IPC: G01C19/5769 ,  G01C19/5783 ,  G01P3/46 ,  G01P15/08

CPC classification number: G01C19/5769 ,  G01C19/5783 ,  G01P15/08 ,  G01P3/46

Abstract: An apparatus for producing signals indicative of both a Coriolis rate and an acceleration along a preferred axis while decoupling extraneous vibration and motion that would introduce errors into the signals, and a driving mechanism for vibrating the apparatus at a dither frequency. The apparatus includes a parallelogram frame (50) including two accelerometer support surfaces (24, 26) on which are mounted two accelerometers (20 and 22) having their sensitive axes in parallel alignment. The accelerometer support surfaces are connected to opposite ends of a flex member (52), which includes six flexures (32, 34, 36, 38, 40, 42) having parallel bending axes. Two of the flexures (34, 38) are disposed at opposite ends of one side of each flexure member, and have a "long" axis that is substantially parallel to the sensitive axes of the accelerometers and aligned with a line connecting their centers of percussion. The centers of mass of the accelerometers and their associated supporting surfaces are coincident with the centers of percussion, and are rigidly connected by the two flexures and by one side (30) of each flex member. This solid metal path between the centers of percussion minimizes common mode errors. A driving mechanism (64) is connected to the parallelogram frame and is opertive to drive the accelerometers at a desired frequency, causing them to vibrate back and forth in a direction substantially transverse to their sensitive axes. The driving mechanism includes a mounting plate (72) and a coil frame (66) on which are mounted two electromagnetic coils (70) having a "C" shaped core (80). The driving mechanism is mounted so that the core faces a pole piece (84) attached to the parallelogram frame and its moment of inertia is trimmed to equal that of the parallelogram frame. It is connected to the parallelogram by a link (88) and provides a reactionless driving force.

公开(公告)号：US4697455A

公开(公告)日：1987-10-06

申请号：US853153

申请日：1986-04-16

Applicant: Brian L. Norling

Inventor： Brian L. Norling

IPC: G01P20060101 ,  G01P15/08 ,  G01P15/13

CPC classification number: G01P15/132

Abstract: An accelerometer comprising a proof mass assembly that includes a reed suspended from a support and a cylindrical coil mounted to the reed by a mounting system that minimizes errors due to thermal stress. The mounting system comprises at least three mounting elements. Each mounting element has first and second ends, and a resilient intermediate portion. The first end of each mounting element is connected to the coil, the second end of each mounting element is connected to the reed, and the intermediate portion of each mounting element provides a low resistance to relative movement between the coil and reed in a radial direction, and a high resistance to relative movement between the coil and reed in directions normal to the radial direction. The reed preferably comprises fused quartz, and the mounting system preferably comprises a fused quartz base mounted directly to the reed and connected to the second end of each mounting element. The coil may be mounted on a coil form that is connected directly to the first end of each mounting element.

Abstract translation: 一种加速度计，包括一个检测质量组件，该检测质量组件包括从支撑件悬挂的簧片和通过安装系统安装到该钢筘上的圆柱形线圈，该安装系统使由于热应力引起的误差最小化。 安装系统包括至少三个安装元件。 每个安装元件具有第一和第二端以及弹性中间部分。 每个安装元件的第一端连接到线圈，每个安装元件的第二端连接到簧片，并且每个安装元件的中间部分对径向方向上的线圈和簧片之间的相对运动提供低电阻 ，并且在垂直于径向方向的方向上对线圈和簧片之间的相对运动具有很高的抵抗力。 簧片优选地包括熔融石英，并且安装系统优选地包括直接安装到簧片并连接到每个安装元件的第二端的熔融石英基座。 线圈可以安装在直接连接到每个安装元件的第一端的线圈形式上。

公开(公告)号：US4694119A

公开(公告)日：1987-09-15

申请号：US687910

申请日：1984-12-31

Applicant: Johannes B. Groenewegen

Inventor： Johannes B. Groenewegen

IPC: G01D11/24 ,  G11B33/14 ,  G12B17/06 ,  H05K5/02 ,  H05K7/00 ,  H05K5/04

CPC classification number: H05K7/005 ,  G11B33/142 ,  H05K5/0213

Abstract: Solid state memory devices employed in crash survivable flight data recorders must be thermally insulated to prevent loss of stored data if the aircraft burns. To provide adequate thermal isolation at minimal size, the solid state electronic memory devices (26) are encapsulated in a synthetic organic wax or pentaerythritol (28) that exhibits a phase transition at a temperature: (a) above the normal operating temperature of the memory unit (10); and below the maximum acceptable peak temperature for the memory devices (26). The synthetic organic wax of pentaerythritol (28) is surrounded by a thermal liner (18) constructed of solid thermal insulating material. A metal enclosure (12) houses and protects the thermal liner (18), the synthetic organic was or pentaerythritol (28) and the memory devices (26).

Abstract translation: 在碰撞存活飞行数据记录仪中使用的固态存储器件必须进行绝热，以防止飞机燃烧时存储的数据丢失。 为了在最小尺寸下提供足够的热隔离，固态电子存储器件（26）被封装在合成有机蜡或季戊四醇（28）中，该合成有机蜡或季戊四醇（28）在高于存储器的正常工作温度的温度（a） 单位（10）; 并且低于存储器件（26）的最大可接受峰值温度。 季戊四醇（28）的合成有机蜡被由固体绝热材料构成的热衬套（18）包围。 金属外壳（12）容纳和保护热衬套（18），合成有机物或季戊四醇（28）和存储装置（26）。

公开(公告)号：US4675823A

公开(公告)日：1987-06-23

申请号：US560073

申请日：1983-12-09

Applicant: Lyle J. Noland, deceased

Inventor： Lyle J. Noland, deceased

IPC: G01C5/00 ,  G01C21/00 ,  G06F15/50

CPC classification number: G01C5/005

Abstract: A ground proximity warning system utilizes geographic position data to alter the warning criteria as is required by the terrain features of particular geographic areas. To determine whether the aircraft is within a particular geographic area, the world is subdivided into latitude bands that are in turn subdivided into non-overlapping zones by predetermined lines of longitude, with the position of each zone being defined by the latitude and longitude coordinates of one of its corners. The zones are further defined by regions which may overlap other zones. The regions are limited in size, and their positions are also defined by the locations of one of their corners. The regions are further subdivided into one or more geographic areas that are defined by their shapes and locations within the region. Inputs from the navigational system of the aircraft are used successively to determine whether the aircraft is in a particular latitude band, zone, region and area, and adjustments to the warning criteria are made to optimize the performance of the warning system for the area in which the aircraft is flying. A "snapshot" is made over known territory to verify the validity of the barometric altitude signal before any modification to the warning criteria is made.

Abstract translation: 地面接近警报系统利用地理位置数据来改变特定地理区域的地形特征所要求的警告标准。 为了确定飞机是否在特定地理区域内，世界被细分为纬度带，纬度带又被细分为非重叠区域，经过预定的经度线，每个区域的位置由纬度和纬度坐标定义 其中一个角落。 这些区域进一步由可能与其他区域重叠的区域限定。 这些地区的大小有限，他们的位置也由他们的一个角落的位置来定义。 这些区域进一步细分为一个或多个由它们在该区域内的形状和位置定义的地理区域。 连续使用飞机导航系统的输入来确定飞机是否处于特定的纬度带，区域，区域和区域，并且对警告标准进行调整，以优化其中的警告系统的性能 飞机正在飞行。 在已知区域之前进行“快照”，以在对警告标准进行任何修改之前验证气压高度信号的有效性。

公开(公告)号：US4674051A

公开(公告)日：1987-06-16

申请号：US736453

申请日：1985-05-21

Applicant: Michael T. Fischer

Inventor： Michael T. Fischer

IPC: G01C21/00 ,  G01S1/04 ,  G01S1/08 ,  G01S5/02 ,  G01S19/25 ,  G08G5/00 ,  G01S5/00 ,  G06F15/50

CPC classification number: G01S5/02 ,  G01C21/00

Abstract: A system for determining the closest navigation point to an aircraft utilizes a sphere of influence principle wherein the earth is subdivided into a plurality of geographic areas, for example, one quarter degree squares of latitude and longitude. An identifier such as an index number of the closest navigation point to each square is stored in a look up table. Position information from the navigation system of the aircraft is used to address the look up table to retrieve the appropriate index number which is then used to address a second look up table that contains information defining the closest navigation point.

Abstract translation: 用于确定与航空器最接近的导航点的系统利用影响范围原理，其中地球被细分为多个地理区域，例如纬度和经度的四分之一度的四分之一平方。 诸如到每个正方形最接近的导航点的索引号的标识符被存储在查找表中。 来自飞行器的导航系统的位置信息用于寻址查找表以检索适当的索引号，该索引号然后用于寻址包含定义最接近的导航点的信息的第二查询表。

公开(公告)号：US4644494A

公开(公告)日：1987-02-17

申请号：US577215

申请日：1984-02-06

Applicant: Hans R. Muller

Inventor： Hans R. Muller

IPC: B64D47/00 ,  G06F17/40 ,  G11C5/00 ,  G11C7/00 ,  G11C16/06 ,  G11C16/20 ,  G11C16/22 ,  G11C16/30 ,  G11C17/00 ,  G11C29/00 ,  G06F3/00 ,  G06F13/00

CPC classification number: G11C29/765 ,  G11C16/06 ,  G11C16/20 ,  G11C16/225 ,  G11C16/30

Abstract: A memory unit for a aircraft flight data recorder system uses an electronically erasable solid state memory for storing the flight data and a memory controller circuit are housed in a penetration resistant, thermally insulated enclosure. Power dissipation within the insulated enclosure is minimized by an external switching circuit that applies operating potential to the solid state memory only when data are being transferred to and from the memory circuit. A data protection circuit, located within the insulated enclosure inhibits memory write and erase operations whenever the system operating potential falls below a predetermined level. In continuously storing flight data, the oldest stored data is overwritten with newly arriving flight data and the memory controller maintains an erased boundary that defines the beginning and end of the recorded data. A power monitor circuit, located outside the insulated enclosure, resets the memory controller to the erased boundary following a power interruption. A dedicated portion of the memory space is utilized to store the address of faulty memory locations (detected during the data storage sequence) and stores the beginning and ending memory address of selected portions of the data record. The memory controller is sequenced to skip both the faulty memory locations and memory storage locations associated with the selected portions of the data record when new flight data is being stored.

Abstract translation: 用于飞机飞行数据记录器系统的存储器单元使用电子可擦除固态存储器来存储飞行数据，并且存储器控制器电路容纳在防穿透绝热外壳中。 只有当数据传输到存储器电路和从存储器电路传输时，外部开关电路才能将绝缘外壳内的功率消耗降至最低。 位于绝缘外壳内的数据保护电路每当系统工作电位低于预定电平时就禁止存储器写入和擦除操作。 在连续存储飞行数据时，最新的存储数据被新到达的飞行数据覆盖，并且存储器控制器保持定义记录数据的开始和结束的擦除边界。 位于绝缘外壳外部的电源监控电路在电源中断后将存储器控制器复位到擦除的边界。 存储器空间的专用部分用于存储故障存储器位置的地址（在数据存储序列期间检测），并存储数据记录的选定部分的开始和结束存储器地址。 当存储新的航班数据时，存储器控制器被排序以跳过与数据记录的选定部分相关联的故障存储器位置和存储器存储位置。